固体火箭技术Issue(3)：301-307,7.DOI:10.7673/j.issn.1006-2793.2015.03.001
基于新型滑模控制方法的再入飞行器姿态控制律设计
Design of a novel sliding mode controller for the attitude control of reentry vehicle
摘要
Abstract
A novel sliding mode control method was proposed in this paper,which is not only capable of improving the robust⁃ness of the existing control law,but can also effectively attenuate chattering.In the design process,a novel dynamic sliding mode sur⁃face was designed firstly based on the nominal system and the existing control law.Then the super⁃twisted algorithm was improved.A fast continuous and finite time convergence algorithm was obtained,which was adopted as the novel reaching law for the first time. The reaching law combined with the sliding mode surface can greatly enhance the robustness of the existing control law.In addition, since the sliding mode switching law is continuous,the chattering was greatly attenuated. The proposed method was then applied to attitude tracking control of reentry vehicle and the robustness of the existing control law was effectively enhanced under large dis⁃turbance.Finally,the effectiveness of the method was demonstrated through simulation.关键词
滑模控制/超扭曲/再入飞行器/动态滑模面/抖振抑制Key words
siding mode control/super-twisting algorithm/reentry vehicle/dynamic sliding surface/chattering attenuate分类
军事科技引用本文复制引用
李宪强,周军,郭建国..基于新型滑模控制方法的再入飞行器姿态控制律设计[J].固体火箭技术,2015,(3):301-307,7.基金项目
国家自然基金（61304238）；国家863计划（2012AA120602）。 （）
